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Full-scale semispan tests of a business-jet wing with a natural laminar flow airfoilA full-scale semispan model was investigated to evaluate and document the low-speed, high-lift characteristics of a business-jet class wing that utilized the HSNLF(1)-0213 airfoil section and a single-slotted flap system. Also, boundary-layer transition effects were examined, a segmented leading-edge droop for improved stall/spin resistance was studied, and two roll-controlled devices were evaluated. The wind-tunnel investigation showed that deployment of single-slotted, trailing-edge flap was effective in providing substantial increments in lift required for takeoff and landing performance. Fixed-transition studies to investigate premature tripping of the boundary layer indicated no adverse effects in lift and pitching-moment characteristics for either the cruise or landing configuration. The full-scale results also suggested the need to further optimize the leading-edge droop design that was developed in the subscale tests.
Document ID
19910020784
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Hahne, David E. (NASA Langley Research Center Hampton, VA, United States)
Jordan, Frank L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:3133
NASA-TP-3133
L-16905
Accession Number
91N30098
Funding Number(s)
PROJECT: RTOP 505-61-41-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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